74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il) Reynolds number: 500,000 Max Cl/Cd: 116.23 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74130wp2mod-il-500000.txt Download as CSV file: xf-fx74130wp2mod-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: 74-130 WP2 MOD
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1198 0.09603 0.09316 -0.0862 0.8385 0.0133
-11.000 -0.1762 0.09931 0.09621 -0.0967 0.8458 0.0127
-10.750 -0.1708 0.09613 0.09304 -0.0980 0.8446 0.0128
-10.500 -0.1626 0.09367 0.09059 -0.0986 0.8433 0.0134
-10.250 -0.1576 0.09059 0.08752 -0.1000 0.8419 0.0136
-10.000 -0.1530 0.08761 0.08455 -0.1013 0.8401 0.0144
-9.750 -0.1497 0.08434 0.08129 -0.1028 0.8385 0.0148
-9.500 -0.1468 0.08100 0.07796 -0.1045 0.8370 0.0145
-9.250 -0.1450 0.07759 0.07455 -0.1062 0.8356 0.0153
-9.000 -0.1446 0.07394 0.07091 -0.1083 0.8339 0.0160
-8.750 -0.1459 0.07013 0.06713 -0.1105 0.8320 0.0164
-8.500 -0.1502 0.06601 0.06306 -0.1135 0.8296 0.0165
-8.250 -0.1607 0.06159 0.05866 -0.1166 0.8262 0.0168
-8.000 -0.1741 0.05846 0.05548 -0.1164 0.8226 0.0166
-7.750 -0.1418 0.04258 0.03964 -0.1106 0.8146 0.0183
-7.500 -0.1467 0.03932 0.03629 -0.1101 0.8123 0.0183
-7.250 -0.1491 0.03597 0.03280 -0.1093 0.8101 0.0184
-7.000 -0.1479 0.03263 0.02929 -0.1084 0.8082 0.0184
-6.750 -0.1617 0.02544 0.02185 -0.1072 0.8064 0.0190
-6.500 -0.1551 0.02205 0.01836 -0.1065 0.8046 0.0196
-6.250 -0.1425 0.01978 0.01602 -0.1060 0.8025 0.0202
-6.000 -0.1284 0.01763 0.01373 -0.1054 0.8002 0.0209
-5.750 -0.1125 0.01556 0.01152 -0.1047 0.7980 0.0219
-5.500 -0.0948 0.01360 0.00934 -0.1040 0.7960 0.0232
-5.250 -0.0742 0.01196 0.00743 -0.1032 0.7942 0.0253
-4.250 0.0223 0.01857 0.01232 -0.1057 0.7915 0.0190
-4.000 0.0470 0.01615 0.00976 -0.1050 0.7893 0.0159
-3.750 0.0725 0.01488 0.00837 -0.1044 0.7868 0.0158
-3.500 0.0981 0.01402 0.00743 -0.1039 0.7844 0.0164
-3.250 0.1238 0.01333 0.00667 -0.1035 0.7822 0.0170
-3.000 0.1512 0.01312 0.00640 -0.1036 0.7803 0.0183
-2.750 0.1760 0.01231 0.00549 -0.1031 0.7785 0.0194
-2.500 0.2011 0.01180 0.00494 -0.1028 0.7760 0.0207
-2.250 0.2273 0.01145 0.00457 -0.1026 0.7731 0.0247
-2.000 0.2502 0.01022 0.00412 -0.1025 0.7704 0.2566
-1.750 0.2687 0.00858 0.00405 -0.1017 0.7679 0.7079
-1.500 0.2929 0.00894 0.00450 -0.1003 0.7658 0.8071
-1.250 0.3176 0.00917 0.00471 -0.0992 0.7635 0.8266
-1.000 0.3400 0.00934 0.00491 -0.0976 0.7598 0.8435
-0.750 0.3618 0.00951 0.00507 -0.0958 0.7566 0.8608
-0.500 0.3831 0.00956 0.00511 -0.0939 0.7540 0.8718
-0.250 0.4080 0.00955 0.00505 -0.0930 0.7518 0.8787
0.000 0.4328 0.00957 0.00504 -0.0924 0.7488 0.8847
0.250 0.4593 0.00955 0.00501 -0.0923 0.7448 0.8894
0.500 0.4849 0.00946 0.00490 -0.0918 0.7415 0.8923
0.750 0.5129 0.00938 0.00477 -0.0919 0.7388 0.8948
1.000 0.5414 0.00933 0.00468 -0.0923 0.7360 0.8971
1.250 0.5683 0.00927 0.00465 -0.0924 0.7311 0.8994
1.500 0.5975 0.00920 0.00455 -0.0930 0.7274 0.9012
1.750 0.6280 0.00913 0.00444 -0.0938 0.7244 0.9027
2.000 0.6544 0.00906 0.00440 -0.0937 0.7201 0.9042
2.250 0.6814 0.00900 0.00435 -0.0938 0.7154 0.9056
2.500 0.7098 0.00892 0.00426 -0.0941 0.7117 0.9069
2.750 0.7378 0.00888 0.00423 -0.0945 0.7074 0.9082
3.000 0.7651 0.00884 0.00424 -0.0946 0.7019 0.9096
3.250 0.7939 0.00878 0.00418 -0.0951 0.6977 0.9110
3.500 0.8218 0.00878 0.00422 -0.0955 0.6925 0.9122
3.750 0.8500 0.00876 0.00423 -0.0959 0.6869 0.9134
4.000 0.8789 0.00874 0.00422 -0.0964 0.6817 0.9147
4.250 0.9061 0.00871 0.00423 -0.0966 0.6730 0.9161
4.500 0.9327 0.00866 0.00420 -0.0966 0.6622 0.9171
4.750 0.9580 0.00863 0.00416 -0.0962 0.6493 0.9183
5.000 0.9826 0.00867 0.00420 -0.0958 0.6350 0.9196
5.250 1.0071 0.00876 0.00429 -0.0954 0.6223 0.9212
5.500 1.0303 0.00889 0.00440 -0.0947 0.6064 0.9231
5.750 1.0527 0.00908 0.00454 -0.0939 0.5880 0.9249
6.000 1.0763 0.00926 0.00475 -0.0934 0.5740 0.9266
6.500 1.1210 0.00970 0.00522 -0.0920 0.5383 0.9303
6.750 1.1372 0.00999 0.00548 -0.0901 0.5097 0.9328
7.000 1.1472 0.01045 0.00582 -0.0871 0.4649 0.9364
7.250 1.1354 0.01148 0.00646 -0.0802 0.3836 0.9436
7.500 1.1192 0.01269 0.00737 -0.0728 0.3222 0.9542
7.750 1.1116 0.01429 0.00862 -0.0682 0.2498 0.9770
8.000 1.1084 0.01614 0.01008 -0.0651 0.1793 1.0000
8.250 1.1070 0.01798 0.01158 -0.0623 0.1195 1.0000
8.500 1.1093 0.01963 0.01297 -0.0600 0.0754 1.0000
8.750 1.1154 0.02108 0.01424 -0.0582 0.0486 1.0000
9.000 1.1260 0.02225 0.01536 -0.0568 0.0367 1.0000
9.250 1.1378 0.02335 0.01647 -0.0555 0.0292 1.0000
9.500 1.1465 0.02467 0.01778 -0.0539 0.0226 1.0000
9.750 1.1574 0.02586 0.01898 -0.0526 0.0175 1.0000
10.000 1.1640 0.02740 0.02058 -0.0508 0.0131 1.0000
10.250 1.1715 0.02889 0.02211 -0.0492 0.0108 1.0000
10.500 1.1686 0.03124 0.02458 -0.0465 0.0097 1.0000
10.750 1.1782 0.03264 0.02610 -0.0453 0.0093 1.0000
11.000 1.1856 0.03426 0.02781 -0.0438 0.0088 1.0000
11.250 1.1925 0.03597 0.02962 -0.0424 0.0085 1.0000
11.500 1.1993 0.03777 0.03152 -0.0410 0.0081 1.0000
11.750 1.2076 0.03946 0.03330 -0.0398 0.0077 1.0000
12.000 1.2162 0.04120 0.03513 -0.0387 0.0075 1.0000
12.250 1.2255 0.04287 0.03688 -0.0378 0.0071 1.0000
12.500 1.2343 0.04462 0.03869 -0.0370 0.0068 1.0000
12.750 1.2416 0.04668 0.04085 -0.0360 0.0065 1.0000
13.000 1.2491 0.04904 0.04336 -0.0348 0.0063 1.0000
13.250 1.2583 0.05150 0.04601 -0.0337 0.0062 1.0000
13.500 1.2652 0.05494 0.04976 -0.0324 0.0061 1.0000
13.750 1.2667 0.05855 0.05362 -0.0314 0.0061 1.0000
14.000 1.2659 0.06155 0.05682 -0.0308 0.0060 1.0000
14.250 1.2627 0.06509 0.06058 -0.0302 0.0060 1.0000
14.500 1.2558 0.06927 0.06499 -0.0299 0.0060 1.0000
14.750 1.2460 0.07393 0.06988 -0.0298 0.0059 1.0000
15.000 1.2344 0.07891 0.07510 -0.0302 0.0059 1.0000
15.250 1.2183 0.08491 0.08132 -0.0310 0.0060 1.0000
15.500 1.2013 0.09117 0.08781 -0.0325 0.0060 1.0000
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